NACA23012


Direct link: NACA23012
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (573) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
NACA23012
Family: NACA 5-digit
Max thickness: 11.9% at x = 30.30% chord
Max camber: 1.3% at x = 14.66% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
Wind Tunnel (NACA-TR-824)
AeroFoil
XFOIL ncrit=9

Notes:


Coordinates generated by JavaFoil
Wind tunnel data from NACA TR-824 as digitized by Gregory P.D. Siemens in 1994 at the University of Saskatchewan.
The digitized TR-824 data has been processed and interpolated to generate all the plots and can not be guaranteed to be an exact match to the TR-824 plots.